CN108032078B - An assembly device for a low-pressure turbine shaft-disc assembly of an aero-engine - Google Patents

An assembly device for a low-pressure turbine shaft-disc assembly of an aero-engine Download PDF

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CN108032078B
CN108032078B CN201711204337.4A CN201711204337A CN108032078B CN 108032078 B CN108032078 B CN 108032078B CN 201711204337 A CN201711204337 A CN 201711204337A CN 108032078 B CN108032078 B CN 108032078B
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turbine shaft
support rod
turbine
tightening
type
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CN108032078A (en
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高航
周天
周天一
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Dalian University of Technology
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Dalian University of Technology
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
    • B23P19/10—Aligning parts to be fitted together
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
    • B23P19/04—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes for assembling or disassembling parts
    • B23P19/06—Screw or nut setting or loosening machines

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  • Mechanical Engineering (AREA)
  • Jigs For Machine Tools (AREA)
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Abstract

The invention discloses an assembly device of a low-pressure turbine shaft-disc assembly of an aero-engine, which comprises a turbine clamp, a turbine shaft posture adjusting and butting system, a transposition type screwing system and a lathe bed. The turbine fixture realizes the horizontal installation of the axis of the turbine unit body; the turbine shaft posture-adjusting butt joint system realizes parallel calibration movement and concentric calibration movement of the turbine shaft relative to the contact end surface of the connecting disc and realizes feed butt joint movement of the turbine shaft relative to the connecting disc; the transposition type screwing system realizes transposition of the screwing shaft to screwing stations corresponding to the circumferentially distributed bolts. The invention adopts the installation mode that the axis of the low-pressure turbine shaft and the disc is horizontal, realizes the centering positioning and calibration of the turbine shaft relative to the connecting disc and the correct and close fit of the end face, and improves the butt joint assembly precision. The invention adopts a transposition type tightening system, and the bolt pretightening force deviation can be effectively controlled by applying the tightening shaft, so that the tightening quality is ensured; and the gantry type moving table is adopted, so that the problem of motion interference in the feeding process of the screwing system is solved.

Description

A kind of assembly device of aero-engine low-pressure turbine shaft-disk component
Technical field
The invention belongs to Automated assembly technical field, in particular to a kind of aero-engine low-pressure turbine shaft-disk component Assembly device.
Background technique
In aero-engine, low-pressure turbine shaft passes through front end flange structure and low-pressure turbo unit body end portion terminal pad phase The power transmitting of Low Pressure Turbine Rotor is realized in assembly.Outer as suffered by Low Pressure Turbine Rotor to carry greatly, axis-disk component is withstood up to The driving torque of tens of tons of axial force and tens of thousands of oxen rice, and its coupling part belongs to abrupt change of cross-section key rapid wear position, therefore Axis-disk component assembly performance is the important factor in order of engine operational reliability.
In low-pressure turbine shaft-disk component assembling process, low-pressure turbine shaft-disk need to carry out relative pose adjustment and calibration, The two is fastened to docking cooperation is carried out along axial direction after just eventually by the circumferential bolt tightening way that is evenly distributed with.It is domestic at present main Manually-operated mode is cooperated to carry out assembly work using fixture, suspender, the movement simple and mechanical mechanism such as accessory and handheld tool Industry, main application apparatus and assembling process are as follows: the biggish low-pressure turbo unit body of volume weight being carried out axis by fixture Turbine wheel shaft is moved to center position by the way of suspender shipment by vertical installation along the vertical direction, complete in the vertical direction At the docking of opposite terminal pad, utensil is tightened using torque spanner etc. and is tightened to along the uniformly distributed bolt group of circumference.On It states in assembling process largely by manual work method, automation assembling device special is not used, has the disadvantage that (1) group Part merging precision is low: length is that the turbine wheel shaft axial dimension of about 2m specification is excessive, causes its microspur using the form that suspender lifts Alignment difficulties are displaced, influence component to heart precision；It is difficult to realize its pose adjustment by mechanical mechanism in vertical turbine wheel shaft, It cannot achieve the flexible assembly requirement for adapting to pairing contact surface type surface error, it is difficult to guarantee that contact surface correctly fits closely； (2) torque spanner mode hand-manipulated tightens unstable quality, and bolt pretightening deviation up to 25%-50% causes under operating condition Weak connecting portion bolt easily loosens；Pretightning force deviation can be effectively controlled to 10% using numerical control tightening axle hereinafter, but because tightening Working space limitation, tightening axle axial feed mechanism are easily interfered with structures such as suspender, fixtures, and apply mechanical arm as stubborn The mode of mandrel sideway feed mechanism the problems such as there are at high cost, rigidity is low and low efficiency；(3) existing assembly equipment largely relies on Manual operation, operating efficiency is low, and assembly consistency is poor；Worker is caused to observe and operate using the vertical assembly method of existing equipment Difficulty requires craftsmanship high, large labor intensity.
Summary of the invention
To solve the above-mentioned problems of the prior art, the present invention provides a kind of aero-engine low-pressure turbine shaft-disk group The assembly device of part, meets the component high-precision docking of turbine wheel shaft-disk and bolt consistency tightens requirements, have that work efficiency is high with Easy to operate feature realizes aero-engine low-pressure turbine shaft-disk high-performance assembly.
The technical scheme is that a kind of assembly device of aero-engine low-pressure turbine shaft-disk component, including turbine Fixture, turbine wheel shaft posture adjustment docking system, indexing type tightening system and lathe bed.
The turbine fixture is located at lathe bed end, realizes that the axis of turbine unit body is the fixed installation of horizontal direction.
The turbine wheel shaft posture adjustment docking system is located in the middle part of lathe bed, by roller type claw I, turbine wheel shaft support rod I, support Rod bearing I, roller type claw II, turbine wheel shaft support rod II, support rod bearing I I, turbine wheel shaft pose adjust platform, turbine wheel shaft pose Adjust platform pedestal and linear rail system I composition；The turbine wheel shaft bottom end support rod I is mounted on turbine axle position by support rod bearing I Appearance adjusts end portion, and turbine wheel shaft support rod I carries out 90 ° of rotations around support rod bearing I, that is, has vertically and horizontally two works Position realizes that turbine wheel shaft support function and indexing type tightening system feeding process avoid function respectively；Roller type claw I is located at turbine The top axis support rod I is equipped with multiple circumferentially distributed idler wheels on roller type claw I, realizes that the centering to turbine shaft tail end is pressed from both sides Tightly；The turbine wheel shaft bottom end support rod II is mounted on turbine wheel shaft pose by support rod bearing I I and adjusts platform the other end, turbine wheel shaft branch Strut II carries out 90 ° of rotations around support rod bearing I I, that is, has vertically and horizontally two stations, realizes turbine wheel shaft support respectively Function and indexing type tightening system feeding process avoid function；Roller type claw II is located at the top turbine wheel shaft support rod II, idler wheel Multiple circumferentially distributed idler wheels are installed on formula claw II, realize that the centering to turbine wheel shaft front end clamps, roller type claw I centering Axis and roller type claw II centering axis are coaxial in the horizontal plane, realize the axis to turbine wheel shaft for the installation of horizontal direction； Turbine wheel shaft pose adjustment platform is mounted on above turbine wheel shaft pose adjustment platform pedestal, and there is opposite turbine wheel shaft pose to adjust platform pedestal water Plane rotation, vertical plane pitching, horizontal shifting and vertical lifting function, realize the turbine installed on turbine wheel shaft pose adjustment platform Contact face collimation movement of the axis with respect to terminal pad and concentric alignment movement, linear rail system I are installed on lathe bed, position In the inside of linear rail system II, turbine wheel shaft pose adjustment platform is mounted on linear rail system II, linear rail system I fortune It is dynamic to be oriented parallel to terminal pad axis direction, realize that movement is docked in feeding of the turbine wheel shaft with respect to terminal pad.
The indexing type tightening system is by planer-type mobile station, tightening axle, tightening axle installation bearing and linear guide system The II that unites is formed；Linear rail system II is installed on lathe bed two sides, and planer-type mobile station is mounted on linear rail system II, straight line The guide track system II direction of motion is parallel to terminal pad axis direction, before realizing that indexing type tightening system is fed to from turbine shaft tail end Hold workspace, during feed motion the aerial part of planer-type mobile station across turbine wheel shaft pose adjust platform, and be in water Space interference does not occur for turbine wheel shaft support rod I, the turbine wheel shaft support rod II of flat station；Tightening axle installation bearing is located at planer-type shifting Above dynamic platform, single or multiple tightening axles are mounted on tightening axle installation bearing, tightening axle install bearing rotation axis with connect Disk axis is coaxial, realizes that tightening axle was indexed into corresponding circle distribution bolt tightens station.
Compared with prior art, beneficial effects of the present invention are as follows:
1, the present invention use low-pressure turbine shaft-disk axis level mounting means, be convenient in docking operation to length compared with Big low-pressure turbine shaft carries out the accurate adjustment of position and posture, realizes that turbine wheel shaft positions calibration and end to the heart with respect to terminal pad Face correctly fits closely, and improves Butt Assembling precision.
2, the present invention uses indexing type tightening system, and single or multiple tightening axles, which are rotated to the mode of station, improves operation effect Bolt pretightening deviation can be effectively controlled using tightening axle, it is ensured that tightens quality in rate；Turbine wheel shaft is cooperated using planer-type mobile station Support rod I, turbine wheel shaft support rod II successively avoid mode, solve the problems, such as movement interference during tightening system feeding.
3, the present invention has the characteristics that structure static rigidity is high and kinetic stability is good, and each functional component is rationally distributed, whole Body is compact-sized.
4, the present invention has the characteristics that high degree of automation, improves working efficiency, reduces craftsmanship's requirement and labour is strong Degree.
5, the present invention sets the structure by changing axis, disk module fixture, and it is low to be suitable for plurality of specifications model aero-engine Turbine wheel shaft-disk component assembly is pressed, axis-disk component assembly of other similar structures forms is also applied for, has compared with high scalability.
Detailed description of the invention
Fig. 1 is aero-engine low-pressure turbine shaft-disk assembly mounting device structural schematic diagram.
Fig. 2 is the structural schematic diagram of turbine wheel shaft posture adjustment docking system.
Fig. 3 is the structural schematic diagram of indexing type tightening system.
Fig. 4 is the operation schematic diagram that application apparatus carries out the adjustment of turbine wheel shaft pose.
Fig. 5 is the operation schematic diagram that application apparatus carries out turbine wheel shaft docking prepackage.
Fig. 6 is the operation schematic diagram that application apparatus carries out that planer-type mobile station is fed to the front end workspace first step.
Fig. 7 is that application apparatus progress planer-type mobile station is fed to front end workspace second step and tightening axle indexing type operation Operation schematic diagram.
In figure: 1, turbine fixture, 2, turbine wheel shaft posture adjustment docking system, 3, indexing type tightening system, 4, lathe bed, 5, turbine list First body, 6, roller type claw I, 7, turbine wheel shaft support rod I, 8, support rod bearing I, 9, roller type claw II, 10, turbine wheel shaft support Bar II, 11, support rod bearing I I, 12, turbine wheel shaft pose adjustment platform, 13, turbine wheel shaft pose adjustment platform pedestal, 14, linear guide System I, 15, turbine wheel shaft, 16, terminal pad, 17, planer-type mobile station, 18, tightening axle, 19, tightening axle installation bearing, 20, straight line Guide track system II.
Specific embodiment
A specific embodiment of the invention is described in detail below in conjunction with technical solution and attached drawing.
As shown in Figure 1-3, a kind of aero-engine low-pressure turbine shaft-disk assembly mounting device, including turbine fixture 1, whirlpool Wheel shaft posture adjustment docking system 2, indexing type tightening system 3 and lathe bed 4.
As shown in Figure 1, the turbine fixture 1 is located at 4 end of lathe bed, realize that the axis of turbine unit body 5 is level side To fixed installation.
As shown in Fig. 2, the turbine wheel shaft posture adjustment docking system 2 is located at 4 middle part of lathe bed, by roller type claw I6, turbine Axis support rod I7, support rod bearing I 8, roller type claw II9, turbine wheel shaft support rod II10, support rod bearing I I11, turbine wheel shaft Pose adjusts platform 12, turbine wheel shaft pose adjustment platform pedestal 13 and linear rail system I14 composition；The turbine wheel shaft bottom end support rod I7 is logical Cross support rod bearing I 8 be mounted on turbine wheel shaft pose adjustment 12 end of platform, turbine wheel shaft support rod I7 can around support rod bearing I 8 into 90 ° of row rotations, that is, have vertically and horizontally two stations, realizes 15 support function of turbine wheel shaft and indexing type tightening system 3 respectively Feeding process avoids function；Roller type claw I6 is located at the top turbine wheel shaft support rod I10, is equipped on roller type claw I6 multiple Circumferentially distributed idler wheel realizes that the centering to 15 tail end of turbine wheel shaft clamps；The turbine wheel shaft bottom end support rod II10 passes through support rod axis Hold II11 be mounted on turbine wheel shaft pose adjustment 12 the other end of platform, turbine wheel shaft support rod II10 can around support rod bearing I I11 into 90 ° of row rotations, that is, have vertically and horizontally two stations, realizes 15 support function of turbine wheel shaft and indexing type tightening system 3 respectively Feeding process avoids function；Roller type claw II9 is located at the top turbine wheel shaft support rod II10, is equipped on roller type claw II9 Multiple circumferentially distributed idler wheels realize that the centering to 15 front end of turbine wheel shaft clamps, roller type claw I6 centering axis and roller type Claw II9 feels relieved, and axis is coaxial in the horizontal plane, and realization is the installation of horizontal direction to the axis of turbine wheel shaft 15；Turbine wheel shaft pose Adjustment platform 12 is mounted on 13 top of turbine wheel shaft pose adjustment platform pedestal, and there is opposite turbine wheel shaft pose to adjust 13 horizontal plane of platform pedestal The motor functions such as rotation, vertical plane pitching, horizontal shifting and vertical lifting realize the turbine wheel shaft 15 installed thereon with respect to terminal pad 16 movement of connection contact face collimation and concentric alignment movement, turbine wheel shaft pose adjustment platform pedestal 13 pass through linear guide System I14 is installed on lathe bed 4, and the linear rail system I14 direction of motion is parallel to 16 axis direction of terminal pad, realizes turbine wheel shaft Movement is docked in the feeding of 15 opposite terminal pads 16.
As shown in fig. 7, the indexing type tightening system 3 is by planer-type mobile station 17, tightening axle 18, tightening axle installation axle Hold 19 and linear rail system II20 composition；Planer-type mobile station 17 is installed on lathe bed 4 by linear rail system II20, directly The line guide track system II20 direction of motion is parallel to 16 axis direction of terminal pad, realizes indexing type tightening system 3 from 15 tail of turbine wheel shaft End is fed to front end workspace, and the aerial part of planer-type mobile station 17 may extend across the adjustment of turbine wheel shaft pose during feed motion Platform 12, and space interference does not occur with turbine wheel shaft support rod I7, turbine wheel shaft support rod II10 in horizontal station；Tightening axle peace Dress bearing 19 is located at 17 top of planer-type mobile station, and single or multiple tightening axles 18 are mounted on tightening axle installation bearing 19, twist Mandrel installs 19 rotation axis of bearing and 16 axis coaxle of terminal pad, realizes that tightening axle 18 is indexed into corresponding circle distribution bolt Tighten station.
As shown in Fig. 1, Fig. 4-7, working method of the invention is as follows:
(1) workpiece is installed: as shown in Figure 1, turbine unit body 5 is fixedly installed on turbine fixture 1, axis is in level Direction；15 tail end of turbine wheel shaft is mounted on the turbine wheel shaft support rod I7 in vertical station by roller type claw I6, the other end End is mounted on the turbine wheel shaft support rod II10 in vertical station by roller type claw II9, and 15 axis of turbine wheel shaft is in water Square to；
(2) turbine wheel shaft pose adjusts: as shown in figure 4, fixed by the connection for observing and measuring turbine wheel shaft 15 and terminal pad 16 The faces parallel deviation and axle center deviation of position contact surface carry out turbine wheel shaft pose and adjust 12 motion work of platform, pass through turbine wheel shaft Pose adjusts 12 horizontal plane rotation of platform (B shaft), end face of the turbine wheel shaft 15 with respect to terminal pad 16 is realized in vertical plane pitching (A shaft) Collimation adjusts the horizontal shifting (Y linear axis) of platform 12 by turbine wheel shaft pose, vertical lifting (Z linear axis) realizes turbine Concentric alignment of the axis 15 with respect to terminal pad 16；Compare connecting hole circumferential direction phase difference of the turbine wheel shaft 15 with respect to terminal pad 16, driving rolling Idler wheel on wheeled claw drives turbine wheel shaft 15 to rotate (C shaft) along axis, completes connecting hole phase alignment and locks idler wheel；
(3) turbine wheel shaft docking prepackage: as shown in figure 5, driving turbine wheel shaft pose adjustment platform pedestal 13 is along linear rail system Docking of the turbine wheel shaft 15 with respect to terminal pad 16 is completed in I14 feed motion (X linear axis), is attached bolt prepackage；
(4) planer-type mobile station is fed to front end workspace: as shown in fig. 6-7, roller type claw I6 unclamps, turbine wheel shaft branch Strut I7 is around 8 90 ° of the indexing of support rod bearing I to horizontal station, and turbine wheel shaft 15 is by turbine wheel shaft support rod II10 and terminal pad 16 It pre-installs bolt and support is provided, planer-type mobile station 17 is along linear rail system II20 displacement (X linear axis) to turbine wheel shaft support rod Between I7 and turbine wheel shaft support rod II10, turbine wheel shaft support rod I7 is back to vertical work for 90 ° around 8 reverse indexing of support rod bearing I Position, roller type claw I6 are clamped；Roller type claw II9 unclamps, and turbine wheel shaft support rod II10 is around 90 ° of indexing of support rod bearing I I11 To horizontal station, turbine wheel shaft 15 pre-installs bolt by turbine wheel shaft support rod I7 and terminal pad 16 and provides support, planer-type mobile station 17 tighten workspace to 15 front end of turbine wheel shaft along linear rail system II20 displacement (X linear axis)；
(5) tightening axle indexing type operation: as shown in fig. 7, being installed on 17 upper end tightening axle of planer-type mobile station installation bearing Single or multiple tightening axles 18 indexable (C shaft) to corresponding tighten on 19 is tightened at bolt, and tightening axle installs bearing 19 Driving tightening axle 18 is tightened by sequential process indexable (C shaft) to next or one group of bolt is tightened, and so on until It completes whole bolts and tightens work.
The present invention is not limited to the present embodiment, any equivalent concepts within the technical scope of the present disclosure or changes Become, is classified as protection scope of the present invention.

Claims (1)

1.一种航空发动机低压涡轮轴-盘组件的装配装置，其特征在于：包括涡轮夹具(1)、涡轮轴调姿对接系统(2)、转位式拧紧系统(3)和床身(4)；1. An assembly device for a low-pressure turbine shaft-disc assembly of an aero-engine, characterized in that: comprising a turbine clamp (1), a turbine shaft attitude adjustment docking system (2), an index-type tightening system (3) and a bed (4) ); 所述的涡轮夹具(1)位于床身(4)端部，实现涡轮单元体(5)的轴线为水平方向的固定安装；The turbine fixture (1) is located at the end of the bed (4), so as to realize the fixed installation in which the axis of the turbine unit body (5) is a horizontal direction; 所述的涡轮轴调姿对接系统(2)位于床身(4)中部，由滚轮式卡爪I(6)、涡轮轴支撑杆I(7)、支撑杆轴承I(8)、滚轮式卡爪II(9)、涡轮轴支撑杆II(10)、支撑杆轴承II(11)、涡轮轴位姿调整台(12)、涡轮轴位姿调整台底座(13)和直线导轨系统I(14)组成；涡轮轴支撑杆I(7)底端通过支撑杆轴承I(8)安装在涡轮轴位姿调整台(12)端部，涡轮轴支撑杆I(7)围绕支撑杆轴承I(8)进行90°转动，即具有竖直和水平二个工位，分别实现涡轮轴(15)支撑功能和转位式拧紧系统(3)进给过程避让功能；滚轮式卡爪I(6)位于涡轮轴支撑杆I(7)顶端，滚轮式卡爪I(6)上安装有多个周向分布的滚轮，实现对涡轮轴(15)尾端的定心夹紧；涡轮轴支撑杆II(10)底端通过支撑杆轴承II(11)安装在涡轮轴位姿调整台(12)另一端部，涡轮轴支撑杆II(10)围绕支撑杆轴承II(11)进行90°转动，即具有竖直和水平二个工位，分别实现涡轮轴(15)支撑功能和转位式拧紧系统(3)进给过程避让功能；滚轮式卡爪II(9)位于涡轮轴支撑杆II(10)顶端，滚轮式卡爪II(9)上安装有多个周向分布的滚轮，实现对涡轮轴(15)前端的定心夹紧，滚轮式卡爪I(6)定心轴线和滚轮式卡爪II(9)定心轴线在水平面内同轴，实现对涡轮轴(15)的轴线为水平方向的安装；涡轮轴位姿调整台(12)安装在涡轮轴位姿调整台底座(13)上方，具有相对涡轮轴位姿调整台底座(13)水平面摆转、竖直面俯仰、水平横移和竖直升降的功能，实现涡轮轴位姿调整台(12)上安装的涡轮轴(15)相对连接盘(16)的接触端面平行校准运动和同心校准运动，直线导轨系统I(14)安装于床身(4)上，位于直线导轨系统II(20)的内侧，涡轮轴位姿调整台(12)安装在直线导轨系统II(20)上，直线导轨系统I(14)运动方向平行于连接盘(16)轴线方向，实现涡轮轴(15)相对连接盘(16)的进给对接运动；The turbine shaft attitude adjustment and docking system (2) is located in the middle of the bed (4), and is composed of a roller type jaw I (6), a turbine shaft support rod I (7), a support rod bearing I (8), and a roller type clamp. Claw II (9), turbine shaft support rod II (10), support rod bearing II (11), turbine shaft position and attitude adjustment table (12), turbine shaft position and attitude adjustment table base (13) and linear guide system I (14 ) composition; the bottom end of the turbine shaft support rod I (7) is installed on the end of the turbine shaft posture adjustment table (12) through the support rod bearing I (8), and the turbine shaft support rod I (7) surrounds the support rod bearing I (8). ) for 90° rotation, that is, there are two vertical and horizontal stations, respectively realizing the support function of the turbine shaft (15) and the feeding process avoidance function of the index type tightening system (3); the roller-type jaws I (6) are located in At the top of the turbine shaft support rod I (7), a plurality of circumferentially distributed rollers are installed on the roller-type jaws I (6) to realize the centering and clamping of the tail end of the turbine shaft (15); the turbine shaft support rod II (10) ) The bottom end is mounted on the other end of the turbine shaft posture adjustment table (12) through the support rod bearing II (11), and the turbine shaft support rod II (10) rotates 90° around the support rod bearing II (11), that is, it has a vertical Two working stations, straight and horizontal, respectively realize the support function of the turbine shaft (15) and the avoidance function of the indexing tightening system (3) during the feeding process; the roller-type jaw II (9) is located at the top of the turbine shaft support rod II (10) , the roller-type jaw II (9) is equipped with a plurality of circumferentially distributed rollers to realize the centering and clamping of the front end of the turbine shaft (15). The roller-type jaws I (6) center the axis and the roller-type jaws II (9) The centering axis is coaxial in the horizontal plane, so that the axis of the turbine shaft (15) is installed in the horizontal direction; the turbine shaft posture adjustment table (12) is installed above the turbine shaft posture adjustment table base (13) , has the functions of horizontal plane swing, vertical plane pitch, horizontal traverse and vertical lift relative to the turbine shaft position and attitude adjustment table base (13), so as to realize the turbine shaft (15) installed on the turbine shaft position and attitude adjustment table (12). Parallel alignment motion and concentric alignment motion relative to the contact end face of the connecting plate (16), the linear guide system I (14) is installed on the bed (4), located inside the linear guide system II (20), the turbine shaft position and attitude adjustment table (12) Installed on the linear guide rail system II (20), the movement direction of the linear guide rail system I (14) is parallel to the axis direction of the connecting plate (16), so as to realize the feeding and docking motion of the turbine shaft (15) relative to the connecting plate (16). ; 所述的转位式拧紧系统(3)由龙门式移动台(17)、拧紧轴(18)、拧紧轴安装轴承(19)和直线导轨系统II(20)组成；直线导轨系统II(20)安装于床身(4)两侧，龙门式移动台(17)安装在直线导轨系统II(20)上，直线导轨系统II(20)运动方向平行于连接盘(16)轴线方向，实现转位式拧紧系统(3)从涡轮轴(15)尾端进给至前端工作区，进给运动过程中龙门式移动台(17)的架空部分跨过涡轮轴位姿调整台(12)，并与处于水平工位的涡轮轴支撑杆I(7)、涡轮轴支撑杆II(10)不发生空间干涉；拧紧轴安装轴承(19)位于龙门式移动台(17)上方，单个或多个拧紧轴(18)安装在拧紧轴安装轴承(19)上，拧紧轴安装轴承(19)旋转轴线与连接盘(16)轴线同轴，实现拧紧轴(18)转位至对应圆周分布螺栓的拧紧工位。The indexing type tightening system (3) is composed of a gantry type moving table (17), a tightening shaft (18), a tightening shaft mounting bearing (19) and a linear guide rail system II (20); the linear guide rail system II (20) Installed on both sides of the bed (4), the gantry type moving table (17) is installed on the linear guide rail system II (20), and the linear guide rail system II (20) moves in a direction parallel to the axis direction of the connecting plate (16) to achieve indexing The screw-type tightening system (3) is fed from the tail end of the turbine shaft (15) to the front-end working area. During the feeding movement, the overhead part of the gantry-type moving table (17) crosses the turbine shaft posture adjustment table (12), and is connected with the The turbine shaft support rod I (7) and the turbine shaft support rod II (10) in the horizontal position do not interfere in space; the tightening shaft mounting bearing (19) is located above the gantry type mobile table (17), and a single or multiple tightening shafts (18) is installed on the tightening shaft mounting bearing (19), and the rotation axis of the tightening shaft mounting bearing (19) is coaxial with the axis of the connecting plate (16), so that the tightening shaft (18) can be indexed to the tightening station corresponding to the circumferentially distributed bolts .
CN201711204337.4A 2017-11-27 2017-11-27 An assembly device for a low-pressure turbine shaft-disc assembly of an aero-engine Active CN108032078B (en)

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